APPARATUS AND METHODS FOR SEALING COMPONENTS IN GAS TURBINE ENGINES

• US 20160245108A1
• Filed: 02/22/2016
• Published: 08/25/2016
• Est. Priority Date: 02/20/2015
• Status: Active Application

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc), Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc), Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Sippel, Aaron D., Freeman, Ted J.
• Granted Patent: US 10,281,045 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2240/55 Seals
• CPC Class Codes: F16J 15/44 Free-space packings
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An apparatus adapted for use in a gas turbine engine includes a first circumferential member and a second circumferential member. The first circumferential member includes an end portion that defines a recess and includes a first seal surface. The second circumferential member includes an end portion that includes a second seal surface. The end portion of the second circumferential member is configured to be at least partially disposed in the recess of the first circumferential member to collectively form at least a portion of a circumferential assembly of a gas turbine. The first seal surface of the first circumferential member is forms a first seal with a seal member and the second seal surface of the second circumferential member is forms a second seal with the seal member when the end portion of the second circumferential member is disposed in the recess of the first circumferential member.

Claims

1. An apparatus adapted for use in a gas turbine engine, the apparatus comprising

a first circumferential member, an end portion of the first circumferential member defining a recess and including a first seal surface;

and

a second circumferential member, an end portion of the second circumferential member configured to be at least partially disposed within the recess of the first circumferential member, the end portion of the second circumferential member including a second seal surface,

the first circumferential member and the second circumferential forming at least a portion of a circumferential assembly of a gas turbine when the end portion of the second circumferential member is at least partially disposed within the recess of the first circumferential member, the first seal surface configured to form a first seal with a seal member and the second seal surface configured to form a second seal with the seal member when the end portion of the second circumferential member is at least partially disposed within the recess of the first circumferential member.

2. The apparatus of claim 1, wherein a line normal to the first seal surface intersects the second seal surface.

3. The apparatus of claim 1, wherein the first seal surface and the second seal surface define an acute angle.

4. The apparatus of claim 1, wherein the end portion of the first circumferential member includes a protrusion including the first seal surface;

and

the end portion of the second circumferential member defines a recess, the protrusion configured to be disposed within the recess of the second circumferential member when the end portion of the second circumferential member is at least partially disposed within the recess of the first circumferential member.

5. The apparatus of claim 1, wherein the circumferential assembly is any one of a blade track assembly, a vane assembly, a support assembly, or an end wall assembly.

6. The apparatus of claim 1, wherein the seal member has a circular cross-sectional area.

7. The apparatus of claim 1, wherein the first circumferential member is formed from a ceramic matrix composite (CMC) material.

8. The apparatus of claim 1, wherein the end portion of the first circumferential member is a first end portion;

the seal member is a first seal member; and

the first circumferential member includes a second end portion configured to be at least partially disposed within a recess of a third circumferential member, the second end portion of the first circumferential member including a third seal surface configured to form a seal with a second seal member.

9. The apparatus of claim 1, wherein the end portion of the first circumferential member defines the recess having a first portion and a second portion, the first portion of the recess including the first seal surface, the second portion of the recess configured to receive a tab extending from the end portion of the second circumferential member when the end portion of the second circumferential member is at least partially disposed within the recess of the first circumferential member.

10. An apparatus adapted for use in a gas turbine engine, the apparatus comprising

a first circumferential member, an end portion of the first circumferential member including a first seal surface;

and

a second circumferential member, an end portion of the second circumferential member including a second seal surface, the end portion of the second circumferential member configured to be disposed adjacent to the end portion of the first circumferential member such that a line normal to the second seal surface intersects the first seal surface,

the first seal surface configured to form a first seal with a seal member and the second seal surface configured to form a second seal with the seal member when the end portion of the second circumferential member is disposed adjacent to the end portion of the first circumferential member, the first circumferential member, the second circumferential member, and the seal member configured to collectively form at least a portion of a circumferential assembly of a gas turbine when the seal member forms the first seal and the second seal.

11. The apparatus of claim 10, wherein the first seal surface and the second seal surface define an acute angle.

12. The apparatus of claim 10, wherein the end portion of the first circumferential member defines a recess including the first seal surface;

and

the end portion of the second circumferential member configured to be disposed within the recess of the first circumferential member when the end portion of the second circumferential member is disposed adjacent to the end portion of the first circumferential member.

13. The apparatus of claim 10, wherein the first circumferential member includes an inner surface, the end portion of the first circumferential member defines a recess including the first seal surface, the first seal surface being substantially parallel to the inner surface of the first circumferential member;

and

the second circumferential member includes an inner surface, the second seal surface being non-parallel to the inner surface of the second circumferential member, the end portion of the second circumferential member configured to be disposed within the recess of the first circumferential member when the end portion of the second circumferential member is disposed adjacent to the end portion of the first circumferential member,

the inner surface of the first circumferential member and the inner surface of the second circumferential member having a substantially similar radius of curvature such that when the end portion of the second circumferential member is disposed adjacent to the end portion of the first circumferential member, at least the portion of the circumferential assembly has a substantially constant inner diameter.

14. The apparatus of claim 10, wherein the seal member is formed from a ceramic matrix composite (CMC) material.

15. The apparatus of claim 10, wherein the end portion of the first circumferential member is a first end portion;

the seal member is a first seal member; and

the first circumferential member includes a second end portion opposite the first end portion, the second end portion including a third seal surface, the second end portion configured to be disposed adjacent to an end portion of a third circumferential member such that a line normal to the second seal surface intersects a fourth sealing surface, the fourth sealing surface included in the end portion of the third circumferential member, the third seal surface configured to form a seal with a second seal member and the fourth seal surface configured to form a seal with the second seal member when the second end portion of the first circumferential member is disposed adjacent to the end portion of the third circumferential member.

16. The apparatus of claim 10, wherein the end portion of the first circumferential member defines a recess and includes a protrusion, at least one of the recess of the first circumferential member or the protrusion of the first circumferential member including the first seal surface;

the end portion of the second circumferential member defines a recess and includes a protrusion, at least one of the recess of the second circumferential member or the protrusion of the second circumferential member including the second seal surface; and

the protrusion of the first circumferential member configured to be disposed within the recess of the second circumferential member and the protrusion of the second circumferential member configured to be disposed within the recess of the first circumferential member when the end portion of the second circumferential member is disposed adjacent to the end portion of the first circumferential member.

17. A method of assembling an apparatus for use in a gas turbine engine, the method comprising

disposing a seal member against a seal surface of an end portion of a first circumferential member;

and

disposing an end portion of a second circumferential member within a recess defined by the first circumferential member such that a seal surface of the second circumferential member is in contact with the seal member, the first circumferential member and the second circumferential forming at least a portion of a circumferential assembly of a gas turbine.

18. The method of claim 17, wherein the seal member is substantially cylindrical having a circular cross-sectional area.

19. The method of claim 17, wherein a line normal to the seal surface of the first circumferential member intersects the seal surface of the second circumferential member when the end portion of the second circumferential member is disposed within the recess defined by the first circumferential member.

20. The method of claim 17, further comprising disposing at least one of a petroleum jelly or an adhesive about at least a portion of the seal member to at least temporarily retain the seal member against the seal surface of the first circumferential member and against the seal surface of the second circumferential member.